The general objectives of this research are to investigate, identify, and quantify the aerodynamic sources of altitude determination errors of the U. S. Navy's Service Aircraft Instrumentation Package (SAIP) and to make recommendations to remedy these errors. This multi-faceted study includes aero- panel methods, computational fluid dynamics (CFD), wind tunnel testing, and flight test evaluations. The Airflow Sensor Assembly (ASA), a device similar to a calibrated pitot static tube, was intended to meet the SAIP's required specifications for altitude determination. However, the ASA is housed in the five inch diameter body of the SAIP and mounted on a variety of host aircraft. The over-pressure generated by the SAIP body as well as the wing/pylon system engulf the static pressure ports creating altitude errors well out of performance limits. This over-pressure associated with these bodies was apparently not accounted for during design and acquisition and extensive modifications will be needed to offset or eliminate their effectsLieutenant, United States NavyApproved for public release; distribution is unlimited
